Patents by Inventor Hidekatsu Atsumi
Hidekatsu Atsumi has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 11499435Abstract: A stator vane includes a blade body, an outer shroud, and an impingement plate. The outer shroud includes a recess. The impingement plate forms a cavity inside the recess. A communication hole is provided in the impingement plate and the outer shroud. In the impingement plate, a plurality of through holes through which an outer space and a cavity communicate with each other are formed. A second region in which an opening ratio is large and a first region in which an opening ratio is small exist in a surface of the impingement plate.Type: GrantFiled: October 4, 2019Date of Patent: November 15, 2022Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.Inventors: Hidekatsu Atsumi, Hidemichi Koyabu
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Patent number: 11371353Abstract: A method of manufacturing a turbine blade includes forming a blade body divided body constituting a blade body of the turbine blade by a three-dimensional lamination method; individually forming a plurality of shroud divided bodies constituting a shroud of the turbine blade for each of the shroud divided bodies by a three-dimensional lamination method; joining the shroud divided bodies together; and joining the blade body divided body and the shroud divided bodies.Type: GrantFiled: June 22, 2018Date of Patent: June 28, 2022Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.Inventors: Hidekatsu Atsumi, Norihiko Motoyama, Shuji Tanigawa
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Publication number: 20220003124Abstract: A stator vane includes a blade body, an outer shroud, and an impingement plate. The outer shroud includes a recess. The impingement plate forms a cavity inside the recess. A communication hole is provided in the impingement plate and the outer shroud. In the impingement plate, a plurality of through holes through which an outer space and a cavity communicate with each other are formed. A second region in which an opening ratio is large and a first region in which an opening ratio is small exist in a surface of the impingement plate.Type: ApplicationFiled: October 4, 2019Publication date: January 6, 2022Inventors: Hidekatsu ATSUMI, Hidemichi KOYABU
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Patent number: 10890073Abstract: A turbine blade (43a) is provided with a blade main body (51) and a tip shroud (52). The blade main body (51) is provided with a leading edge-side cooling passage (64), a trailing edge-side cooling passage (67), and a middle cooling passage (65). The tip shroud (52) is provided with a first discharge passage (72), a second discharge passage (73), and a third discharge passage (74). The first discharge passage (72) discharges a cooling medium flowing through the leading edge-side cooling passage (64). The second discharge passage (73) discharges a cooling medium flowing through the trailing edge-side cooling passage (67). The third discharge passage (74) discharges a cooling medium flowing through the middle cooling passage (65).Type: GrantFiled: August 23, 2016Date of Patent: January 12, 2021Assignee: MITSUBISHI POWER, LTD.Inventors: Keita Takamura, Satoshi Hada, Hidekatsu Atsumi
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Publication number: 20200208525Abstract: A method of manufacturing a turbine blade includes forming a blade body divided body constituting a blade body of the turbine blade by a three-dimensional lamination method; individually forming a plurality of shroud divided bodies constituting a shroud of the turbine blade for each of the shroud divided bodies by a three-dimensional lamination method; joining the shroud divided bodies together; and joining the blade body divided body and the shroud divided bodies.Type: ApplicationFiled: June 22, 2018Publication date: July 2, 2020Inventors: Hidekatsu ATSUMI, Norihiko MOTOYAMA, Shuji TANIGAWA
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Patent number: 10655478Abstract: A blade main body (51) of a gas turbine is provided with a first cooling passage part (58), a second cooling passage part (59), a column part (60), and a plurality of protrusions. The first cooling passage part (58) is provided at the side near to a leading edge (55). The second cooling passage part (59) is provided at the side near to a trailing edge (56). The column part (60) is provided between the first cooling passage part (58) and the second cooling passage part (59), and is continuously formed between a base part and an end part of the blade main body (51). The protrusions protrude from the inner wall surfaces of the first cooling passage part (58) and the second cooling passage part (59).Type: GrantFiled: August 8, 2016Date of Patent: May 19, 2020Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.Inventors: Keita Takamura, Satoshi Hada, Hidekatsu Atsumi
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Patent number: 10633977Abstract: An end plate of a blade has a gas path surface facing a combustion gas channel side, an end surface along an edge of the gas path surface, a plurality of channels, and a skirt hole. The plurality of channels extend along the direction of a partial end surface, which is a portion of the end surface, and are arranged in a perspective direction with respect to the partial end surface. The skirt hole opens at the partial end surface. The skirt hole communicates with an inside channel, which is the channel of the plurality of channels that is farthest from the partial end surface.Type: GrantFiled: October 19, 2016Date of Patent: April 28, 2020Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.Inventors: Keita Takamura, Saki Matsuo, Yoshifumi Tsuji, Satoshi Hada, Hidekatsu Atsumi
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Patent number: 10376950Abstract: A blade has a blade, passage extending in a blade height direction, a platform passage formed inside a platform, and a communication passage leading from an outer surface of a shaft-mounted part through the platform passage to the blade passage. An inner surface defining an inflow passage portion of the platform passage includes a shaft-side inner surface that faces a gas path side. The shaft-side inner surface spreads in a direction having more of a component of a blade thickness direction than a component of the blade height direction. An inner surface defining the communication passage joins to the shaft-side inner surface.Type: GrantFiled: September 8, 2016Date of Patent: August 13, 2019Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.Inventors: Keita Takamura, Satoshi Hada, Hidekatsu Atsumi, Tomofumi Shintani
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Publication number: 20180274371Abstract: An end plate of a blade has a gas path surface facing a combustion gas channel side, an end surface along an edge of the gas path surface, a plurality of channels, and a skirt hole. The plurality of channels extend along the direction of a partial end surface, which is a portion of the end surface, and are arranged in a perspective direction with respect to the partial end surface. The skirt hole opens at the partial end surface. The skirt hole communicates with an inside channel, which is the channel of the plurality of channels that is farthest from the partial end surface.Type: ApplicationFiled: October 19, 2016Publication date: September 27, 2018Inventors: Keita TAKAMURA, Saki MATSUO, Yoshifumi TSUJI, Satoshi HADA, Hidekatsu ATSUMI
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Publication number: 20180200783Abstract: A blade (50) has a blade, passage (71) extending in a blade height direction (Dwh), a platform passage (81) formed inside a platform (60), and a communication passage (75) leading from an outer surface (93) of a shaft-mounted part (90) through the platform passage (81) to the blade passage (71). An inner surface defining an inflow passage portion (82) of the platform passage (81) includes a shaft-side inner surface (88) that faces a gas path side. The shaft-side inner surface (88) spreads in a direction having more of a component of a blade thickness direction (Dwt) than a component of the blade height direction (Dwh). An inner surface defining the communication passage (75) joins to the shaft-side inner surface (88).Type: ApplicationFiled: September 8, 2016Publication date: July 19, 2018Inventors: Keita TAKAMURA, Satoshi HADA, Hidekatsu ATSUMI, Tomofumi SHINTANI
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Publication number: 20180149024Abstract: A turbine blade (43a) is provided with a blade main body (51) and a tip shroud (52). The blade main body (51) is provided with a leading edge-side cooling passage (64), a trailing edge-side cooling passage (67), and a middle cooling passage (65). The tip shroud (52) is provided with a first discharge passage (72), a second discharge passage (73), and a third discharge passage (74). The first discharge passage (72) discharges a cooling medium flowing through the leading edge-side cooling passage (64). The second discharge passage (73) discharges a cooling medium flowing through the trailing edge-side cooling passage (67). The third discharge passage (74) discharges a cooling medium flowing through the middle cooling passage (65).Type: ApplicationFiled: August 23, 2016Publication date: May 31, 2018Inventors: Keita TAKAMURA, Satoshi HADA, Hidekatsu ATSUMI
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Publication number: 20180128116Abstract: A blade main body (51) of a gas turbine is provided with a first cooling passage part (58), a second cooling passage part (59), a column part (60), and a plurality of protrusions. The first cooling passage part (58) is provided at the side near to a leading edge (55). The second cooling passage part (59) is provided at the side near to a trailing edge (56). The column part (60) is provided between the first cooling passage part (58) and the second cooling passage part (59), and is continuously formed between a base part and an end part of the blade main body (51). The protrusions protrude from the inner wall surfaces of the first cooling passage part (58) and the second cooling passage part (59).Type: ApplicationFiled: August 8, 2016Publication date: May 10, 2018Inventors: Keita TAKAMURA, Satoshi HADA, Hidekatsu ATSUMI
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Patent number: 9677406Abstract: The purpose of the invention is to provide a rotor blade support structure, wherein the concentration of stress near the rotor blade groove in which the rotor blade is embedded is limited even as increase in production cost is limited. A rotor blade support structure, in which rotor blades (30) are embedded in rotor blade grooves (10) provided on a rotor disc (1), wherein the rotor blade groove (10) is provided with circular direction grooves (13) that extend more in the circular direction of the rotor disc than upward from the bottom (14), and shaft center direction grooves (15) that are provided on the end faces (1a, 1b) of the rotor disc (1) in the center of the bottom (14) in the circular direction of the rotor disc and that extend towards the rotor disc shaft center.Type: GrantFiled: October 16, 2012Date of Patent: June 13, 2017Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.Inventors: Tomoyuki Hirata, Eigo Katou, Hidekatsu Atsumi
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Publication number: 20140219806Abstract: The purpose of the invention is to provide a rotor blade support structure, wherein the concentration of stress near the rotor blade groove in which the rotor blade is embedded is limited even as increase in production cost is limited. A rotor blade support structure, in which rotor blades (30) are embedded in rotor blade grooves (10) provided on a rotor disc (1), wherein the rotor blade groove (10) is provided with circular direction grooves (13) that extend more in the circular direction of the rotor disc than upward from the bottom (14), and shaft center direction grooves (15) that are provided on the end faces (1a, 1b) of the rotor disc (1) in the center of the bottom (14) in the circular direction of the rotor disc and that extend towards the rotor disc shaft center.Type: ApplicationFiled: October 16, 2012Publication date: August 7, 2014Applicant: MITSUBISHI HITACHI POWER SYSTEMS, LTD.Inventors: Tomoyuki Hirata, Eigo Katou, Hidekatsu Atsumi